CN103003060B - Modular organization composite beam - Google Patents
Modular organization composite beam Download PDFInfo
- Publication number
- CN103003060B CN103003060B CN201180028703.XA CN201180028703A CN103003060B CN 103003060 B CN103003060 B CN 103003060B CN 201180028703 A CN201180028703 A CN 201180028703A CN 103003060 B CN103003060 B CN 103003060B
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- China
- Prior art keywords
- elongated elements
- skin members
- fibre reinforced
- reinforced plastics
- main body
- Prior art date
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- 239000002131 composite material Substances 0.000 title claims abstract description 41
- 230000008520 organization Effects 0.000 title description 14
- 238000000034 method Methods 0.000 claims abstract description 33
- 229920002430 Fibre-reinforced plastic Polymers 0.000 claims abstract description 30
- 239000011151 fibre-reinforced plastic Substances 0.000 claims abstract description 30
- 210000002615 epidermis Anatomy 0.000 claims description 55
- 210000003491 skin Anatomy 0.000 claims description 49
- 239000000463 material Substances 0.000 claims description 14
- 239000007787 solid Substances 0.000 claims description 7
- 229920003023 plastic Polymers 0.000 claims description 6
- 239000004033 plastic Substances 0.000 claims description 6
- 239000004615 ingredient Substances 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 6
- 230000008859 change Effects 0.000 description 8
- 239000000853 adhesive Substances 0.000 description 5
- 230000001070 adhesive effect Effects 0.000 description 5
- 239000011162 core material Substances 0.000 description 5
- 238000010008 shearing Methods 0.000 description 5
- 239000000835 fiber Substances 0.000 description 4
- 239000003822 epoxy resin Substances 0.000 description 3
- 238000000465 moulding Methods 0.000 description 3
- 229920000647 polyepoxide Polymers 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- 210000001015 abdomen Anatomy 0.000 description 2
- 238000003491 array Methods 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 229920000139 polyethylene terephthalate Polymers 0.000 description 2
- 239000005020 polyethylene terephthalate Substances 0.000 description 2
- 238000002360 preparation method Methods 0.000 description 2
- 230000002787 reinforcement Effects 0.000 description 2
- 229920005989 resin Polymers 0.000 description 2
- 239000011347 resin Substances 0.000 description 2
- SMZOUWXMTYCWNB-UHFFFAOYSA-N 2-(2-methoxy-5-methylphenyl)ethanamine Chemical compound COC1=CC=C(C)C=C1CCN SMZOUWXMTYCWNB-UHFFFAOYSA-N 0.000 description 1
- NIXOWILDQLNWCW-UHFFFAOYSA-N 2-Propenoic acid Natural products OC(=O)C=C NIXOWILDQLNWCW-UHFFFAOYSA-N 0.000 description 1
- 240000007182 Ochroma pyramidale Species 0.000 description 1
- 229920006328 Styrofoam Polymers 0.000 description 1
- BZHJMEDXRYGGRV-UHFFFAOYSA-N Vinyl chloride Chemical compound ClC=C BZHJMEDXRYGGRV-UHFFFAOYSA-N 0.000 description 1
- 238000007596 consolidation process Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005553 drilling Methods 0.000 description 1
- 150000002148 esters Chemical class 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000011152 fibreglass Substances 0.000 description 1
- 239000003365 glass fiber Substances 0.000 description 1
- LNEPOXFFQSENCJ-UHFFFAOYSA-N haloperidol Chemical compound C1CC(O)(C=2C=CC(Cl)=CC=2)CCN1CCCC(=O)C1=CC=C(F)C=C1 LNEPOXFFQSENCJ-UHFFFAOYSA-N 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000010030 laminating Methods 0.000 description 1
- 238000003475 lamination Methods 0.000 description 1
- 230000004899 motility Effects 0.000 description 1
- -1 polyethylene terephthalate Polymers 0.000 description 1
- 229920001296 polysiloxane Polymers 0.000 description 1
- 229920002635 polyurethane Polymers 0.000 description 1
- 239000004814 polyurethane Substances 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000004513 sizing Methods 0.000 description 1
- 239000008261 styrofoam Substances 0.000 description 1
- 229920005992 thermoplastic resin Polymers 0.000 description 1
- 229920001187 thermosetting polymer Polymers 0.000 description 1
- 229920001567 vinyl ester resin Polymers 0.000 description 1
- 125000000391 vinyl group Chemical group [H]C([*])=C([H])[H] 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D99/00—Subject matter not provided for in other groups of this subclass
- B29D99/0003—Producing profiled members, e.g. beams
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
- B29C70/86—Incorporated in coherent impregnated reinforcing layers, e.g. by winding
- B29C70/865—Incorporated in coherent impregnated reinforcing layers, e.g. by winding completely encapsulated
-
- E—FIXED CONSTRUCTIONS
- E04—BUILDING
- E04C—STRUCTURAL ELEMENTS; BUILDING MATERIALS
- E04C3/00—Structural elongated elements designed for load-supporting
- E04C3/02—Joists; Girders, trusses, or trusslike structures, e.g. prefabricated; Lintels; Transoms; Braces
- E04C3/29—Joists; Girders, trusses, or trusslike structures, e.g. prefabricated; Lintels; Transoms; Braces built-up from parts of different material, i.e. composite structures
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03D—WIND MOTORS
- F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor
- F03D1/06—Rotors
- F03D1/065—Rotors characterised by their construction elements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2105/00—Condition, form or state of moulded material or of the material to be shaped
- B29K2105/24—Condition, form or state of moulded material or of the material to be shaped crosslinked or vulcanised
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2105/00—Condition, form or state of moulded material or of the material to be shaped
- B29K2105/24—Condition, form or state of moulded material or of the material to be shaped crosslinked or vulcanised
- B29K2105/243—Partially cured
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/001—Profiled members, e.g. beams, sections
- B29L2031/003—Profiled members, e.g. beams, sections having a profiled transverse cross-section
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/08—Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
- B29L2031/082—Blades, e.g. for helicopters
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2280/00—Materials; Properties thereof
- F05B2280/60—Properties or characteristics given to material by treatment or manufacturing
- F05B2280/6003—Composites; e.g. fibre-reinforced
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2280/00—Materials; Properties thereof
- F05B2280/60—Properties or characteristics given to material by treatment or manufacturing
- F05B2280/6013—Fibres
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2280/00—Materials; Properties thereof
- F05B2280/70—Treatments or modification of materials
- F05B2280/702—Reinforcements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
- F05C2253/00—Other material characteristics; Treatment of material
- F05C2253/04—Composite, e.g. fibre-reinforced
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
- F05C2253/00—Other material characteristics; Treatment of material
- F05C2253/16—Fibres
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
- F05C2253/00—Other material characteristics; Treatment of material
- F05C2253/22—Reinforcements
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P70/00—Climate change mitigation technologies in the production process for final industrial or consumer products
- Y02P70/50—Manufacturing or production processes characterised by the final manufactured product
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49616—Structural member making
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49826—Assembling or joining
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Architecture (AREA)
- Composite Materials (AREA)
- General Engineering & Computer Science (AREA)
- Sustainable Energy (AREA)
- Combustion & Propulsion (AREA)
- Sustainable Development (AREA)
- Life Sciences & Earth Sciences (AREA)
- Civil Engineering (AREA)
- Structural Engineering (AREA)
- Moulding By Coating Moulds (AREA)
- Rod-Shaped Construction Members (AREA)
- Wind Motors (AREA)
- Laminated Bodies (AREA)
Abstract
Modular fibre reinforced plastics flange (5) for structure composite beam (10), said structure composite beam includes being arranged to, by multiple elongated elements (42), the main body (40) that array is formed, wherein the size of main body is substantially determined by the quantity of elongated elements in array and layout, and skin members (20,30) at least partly surrounds array.It addition, structure composite beam includes modular fibre reinforced plastics flange (5) and the shear web (50) being connected on the skin members of modular flange.Also disclose manufacture modular flange and the method for beam, and for manufacturing the kit of modular flange.
Description
Technical field
The present invention relates to modular organization composite beam.Specifically, the present invention relates to at wind wheel
The modular organization composite beam used in machine blade.
Background technology
The construction of big wind turbine blade (length is more than 35 meters) is typically by inside trousers
Form the cantilever beam or box spar strengthened and reinforce and carry out.Currently manufactured wind turbine blade
Method is two half shells that each blade or produce into has separately beam, or produces into tool
There are two half shells of unjointed beam.In both cases, all two half shells along them
Edge is combined to form complete blade.
Structural beams includes flange at two ends, and these flanges are by one (or more generally useful two
Individual) shear web is connected with each other.Flange mainly unidirectional fibre reinforced plastics is made, and resists
Shear web is made up of the most polyaxial (+/-45 °) fibre reinforced plastics.
It is well known that in the art, by flange being molded into each half-shell of trousers
Internal and with shear web, flange is come together to manufacture time then trousers is bonded together
Beam.Alternatively, by separate beam is molded on separate instrument and then when this
A little beams are bonded in trousers make beam when being bonded together.
These methods the most all have many shortcomings.First, if the unidirectional flange of beam is molded into
In trousers, then it is difficult to control exactly the quality of flange material.This is commonly due to flange material
Material causes bad mechanical performance, and this bad mechanical performance causes again increasing for engineering safety
Therefore required material also increases cost.
If beam is separately formed by being molded on separate instrument, then can avoid a part
Disadvantages mentioned above.But, the cost of separate tools increases the totle drilling cost of parts.
No matter in the case of which kind of, if needing new design or slight variation in the design,
The most all must make brand-new instrument, thus add prototype design time and cost, also increase
Introduce the cost of new model.Similarly, if it is considered that use automatization, the then one-tenth of automatization
This general is the highest, because have to process many different beam designs and geometric form at that rate
Shape.
Summary of the invention
Designing in the international monopoly Shen announced of the applicant for modular wind turbine blade
WO 2009/034291 please be described.That application discloses and include multiple standardized group
Become the wind turbine blade of parts, above-mentioned standardized building block for as overall blade,
It is available for providing the design flexibility bigger than traditional manufacturing technology.But, structural beams is designed by it
Amendment be provided only with limit scheme.It is an object of the invention to provide modular organization composite beam,
This modular organization composite beam provides the design flexibility and quality improved, and can be as tradition wind
The part of turbine blade, as a part for modular wind turbine blade or tie at other
Structure application (such as bridge) uses.
Therefore, in first aspect, the modular fiber that the present invention is provided to structure composite beam increases
Strong plastic flange, this flange includes: the main body formed by multiple elongated elements, the plurality of
Elongated elements is arranged to array so that the longitudinal axis of each elongated elements is substantially parallel to one another, its
In, the size of main body is substantially determined by the quantity of elongated elements in array and layout；And,
At least partly surround the skin members of multiple elongated elements in array.
By using multiple elongated elements and external skins to build the main body of flange so that flange
Design can by the array of change elongated elements and the size of skin members and structure easily
Change.The employing of skin members additionally provides the shearing resistance load performance of improvement.
In a preferred embodiment, skin members entirely around the array of elongated elements to carry
For extra supporting and structural integrity.
Skin members preferably includes the first epidermis element and the second epidermis element, the first epidermis unit
Part has recessed form, and the second epidermis element is arranged to be assemblied in the first epidermis element.This
Kind of layout allows to, before assembling the second epidermis element completes skin members, main body is placed on the
In one epidermis element.So, the thickness of main body can change, and the change in size of skin members
The least or be not changed in.
Preferably, skin members includes socket, in order in use to accommodate shear web.This carries
Supply to be attached to flange transmit on shear web and between flange and shear web the letter of load
Just method.
In a preferred embodiment, at least two elongated elements includes different materials.This makes
Obtain and can easily the mechanical performance of flange be changed.
In order to improve shearing resistance load performance further, preferably at least one enhancement layer at least portion
It is located in the array of elongated elements with dividing.
In second aspect, the present invention provides structure composite beam, and it includes: first aspect present invention
Described modular flange；And, the shearing resistance abdomen being connected on the skin members of modular flange
Plate.By this way, it is provided that improvement and more general structure composite beam.
Shear web preferably includes the structural core between two composite layers to provide
Further structural integrity.Composite layer is preferably polyaxial composite.Shearing resistance abdomen
Plate is favourable, because it can be assembled in flange as " open type " sandwich plate, because plate
End is the socket of skin members.It means that with discontinuous method of molding, (this method of molding is wanted
Ask the end of " closed " sandwich plate) contrary, shear web (can be made with continuous working system
Or more), thus reduce production cost and increase motility.
In the third aspect, the present invention provides and forms the modular fiber reinforcement for structure composite beam
The method of plastic flange, the method includes: form main body with multiple elongated elements, the plurality of
Elongated elements is arranged to array so that the longitudinal axis of each elongated elements is substantially parallel to one another, its
In, the size of main body is substantially determined by the quantity of elongated elements in array and layout；And,
Skin members is connected in main body, so that skin members at least partly surrounds in array many
Individual elongated elements.
Method the most also includes: quantity and the layout of selection elongated elements are to limit main body
Size；And, selecting skin members, this skin members is sized so as to substantially
Coordinate the size of main body.In this way it is possible in the case of need not equip new tool
Different size and the flange of mobility is formed easily with standardized parts.
Preferably, skin members includes the first epidermis element and the second epidermis element, the first epidermis
Element has concave form, and the second epidermis element is arranged to be assemblied in the first epidermis element；
Method also includes: main body be located in the first epidermis element；And, the second epidermis element is set
To form the skin members entirely around main body in the first epidermis element.
In fourth aspect, the present invention provides the method forming structure composite beam, and the method includes:
The method using a third aspect of the present invention；And, at least one shear web is connected to mould
On the skin members of block formula flange.
Preferably, in the method for a third aspect of the present invention, or the four directions in the present invention
In the method in face, each ingredient of modular flange or structure composite beam is with the most raw
Product method is made.It reduce production cost and improve quality, because working system is spent less continuously
Time and labor intensity and repeatable higher, thus decrease waste.
Before implementing the method for a third aspect of the present invention and fourth aspect, modular flange
At least one shear web of elongated elements and skin members and structure composite beam preferably place
In solid state or semi-cured state the final form presenting them.Therefore, convex at modular
Edge or structure composite beam assembled before, the shape of elongated elements, skin members and shear web
Substantially fixed with size.Additionally, before modular flange or structure composite beam are assembled,
The main Mechanical of elongated elements, skin members and shear web is substantially fixed.
At the 5th aspect, the present invention is provided to be formed the one-tenth of modular fibre reinforced plastics flange
Set parts, including: being suitable for forming multiple elongated elements of main body, this main body includes being arranged to
Multiple elongated elements of array, wherein, the longitudinal axis of each elongated elements is substantially parallel to one another；
And, multiple skin members, wherein, multiple skin members are sized so as to long
The predetermined quantity of shape element is corresponding.Thus, kit provides for producing different size
Means with the flange of mechanical performance.
The elongated elements of kit and skin members are preferably at solid state or semi-solid preparation
State also presents their final form.
Accompanying drawing explanation
The example of the present invention is described, wherein now with reference to accompanying drawings below:
Fig. 1 illustrates the exploded sketch of a kind of modular organization composite beam part；
Fig. 2 illustrates a kind of modular fibre reinforced plastics flange and the schematic sectional of separate web
Figure；
Fig. 3 illustrates the schematic sectional view of the modular organization composite beam part assembled；
Fig. 4 illustrates the signal of a kind of alternative modular organization composite beam part assembled
Sectional view；And
Fig. 5 illustrates showing of another kind of alternative modular organization composite beam part assembled
Meaning sectional view.
Detailed description of the invention
Fig. 1 illustrates the exploded sketch of modular organization composite beam 10 part.Beam 10
Including the first epidermis element 20 and the second epidermis element 30 and multiple elongated elements 40.Additionally,
Beam 10 includes that two shear webs 50, each shear web 50 include that structural core 52 is with outer
Portion's epidermal area 54.
Structural core 52 can be made with any suitable material, and described material includes that PVC(gathers
Vinyl chloride), PET(polyethylene terephthalate), cork wood or STYROFOAM
Or the most well-known and other structural core material of use.External cuticle layers 54
Mainly include polyaxial (± 45 °) fibre reinforced plastics.External cuticle layers 54 is by adhesive such as
Sqtructural adhesive (such as epoxy resin, polyurethane, acrylic acid, silicone) or with resin as poly-
Ester, vinyl esters, epoxy resin or other structural thermoset or thermoplastic resin are attached to core 52
On.
Elongated elements 40 mainly includes uniaxially fibre reinforced plastics.Elongated elements is typically " pre-
Molding " unidirectional composite material, such as pultrusion part or the prepreg of semi-solid preparation or intermediate section bar
Material so that they see Fig. 2 forming flange 5() before present their net shape or form.
As shown in fig. 1, elongated elements 40 is arranged to array (being 3 × 3 arrays in this case)
To form main body 42, this main body 42 forms the main load-supporting part of flange 5.Elongated elements 40
By sqtructural adhesive or by by a kind of method such as manual lamination method, vacuum injection, vacuum
Consolidation or the similar laminating method used in the art are laminated together and viscous with structural resin
It is combined to form main body 42.
First and second external skins elements 20,30 respectively mainly include polyaxial fiber reinforcement plastic
Material.First epidermis element 20 has the recessed form of U-shaped, and the second epidermis element 30 includes dashing forward
Playing 32, projection 32 limits socket 34 at each external margin of the second epidermis element 30.Insert
Mouth 34 is sized so as to accommodate the edge 56 of shear web 50.
As shown in Figure 2, in the flange 5 assembled, the second epidermis element 30 is assemblied in
In one epidermis element 20.Two epidermis elements 20,30 are formed together entirely around main body 42
Skin members 60.In this example, " entirely around " mean that skin members 60 surrounds master
Body 42 but the end of the most main body covered 42.
The most as shown in Figure 2, the first epidermis element and the second epidermis element 20,30 are processed into one
Sizing is to match with main body 42.The size of main body 42 is by the number of elongated elements in array
Amount and layout limit.In the example shown in Fig. 2, main body 42 includes 3 × 3 arrays, therefore leads
The degree of depth of body 42 is identical with the three of elongated elements 40 times of degree of depth, and the width of main body 42 is substantially
Identical with the three of elongated elements 40 times of width.
Fig. 3 illustrates the flange 5 fitted together with shear web 50.Shear web is assembled to insert
It is attached in mouth 34 and by adhesive such as structural epoxy resins adhesive.As indicated, shear web
The end of shear web 50 " is closed " at 50 positions in socket 34.Case is the most only shown
The upper part of ellbeam 10.It should be understood that another flange 5 can be attached to shear web
To form complete box-girder 10 on the downside of 50.Additionally, shear web 50 can have
The various different degree of depth are to change the degree of depth of box-girder 10.This degree of depth can be along the length of beam
Change, in order to such as form the tapering of wind turbine blade.
Fig. 4 illustrates the alternative structure of one of the upper part of modular organization composite beam 100
Make.In this case, beam 100 is a kind of I-beam, and this I-beam includes being positioned at the second table
Only one shear web 50 in the central socket 134 of skin component 130.Form flange 105
The elongated elements 40,140 of main body 142 include different fiber reinforced plastic materials, therefore
Elongated elements 40 can include such as fiberglass reinforced plastics, and elongated elements 140 can wrap
Include such as carbon fibre reinforced plastic.Different materials elongated elements 40,140 shown in Fig. 4
Layout be only an example, and any other arrange can be according to required mechanical performance choosing
Fixed.
Beam 100 also includes the enhancement layer in main body 42 between the layer of elongated elements 40,140
144.These enhancement layers mainly include polyaxial (± 45 °) fibre reinforced plastics and to flange 105
Extra shearing strength is provided.In any modular organization composite beam as herein described constructs all
Enhancement layer 144 can be included.
Fig. 5 illustrates that the another kind of the upper part of modular organization composite beam 200 is alternative
Structure.Elongated elements 40 and skin members 260 only include elongated partially around array
The epidermis element 220 of element 40a, 40b and 40c.
It should be understood that any quantity can be included in the array forming main body 42,142,242
Elongated elements 40,140, and can be selected of elongated elements in any required layout
The different fibre reinforced materials of what quantity.As such, it is possible to change flange 5,105,205 on demand
Mechanical performance.
Referring back to Fig. 2, if the width of main body 42 keep identical (3 elongated elements width) but
The degree of depth changes (such as, two elongated elements are deep), then can use identical epidermis element 20,
30, then depth difference is by the fact that regulate: the i.e. second epidermis element 30 is assembled to the first epidermis
Until arriving main body 42 in element 20.It is possible if desired to the side to the first epidermis element 20
Face 22 is repaired, in order to remove projection 32 overlapping portion with the second epidermis element 30.It is available for
Selectively, bigger degree of depth main body 42(such as, 4 or more elongated elements deep) can pass through
The variable depth energy that the interaction of the first epidermis element and the second epidermis element 20,30 is provided
Power and be received.In this case, the projection 32 of the second epidermis element 30 can be optionally
Carry out repairing to remove the overlapping portion, side 22 with the first epidermis element 20.
If the change width of main body 42 (such as, two elongated elements width), then it is preferably
There is provided the epidermis element 20,30 of suitable dimension to coordinate the width of main body 42.Elongated elements
40 preferably have standard size to be provided that the standardization chi of one group of epidermis element 20,30
The very little various different array coordinating elongated elements.
Above-mentioned fibre-inforced plastic parts is typically glass fibre as known in the art and increases
Strong plastics or carbon fibre reinforced plastic.But any other suitable fiber reinforced plastic materials is all
Can use.
Claims (17)
1. for a modular fibre reinforced plastics flange for structure composite beam, including:
The main body formed by multiple prefabricated elongated elements, each elongated elements in the plurality of elongated elements is formed by composite, the plurality of elongated elements is arranged to array so that the longitudinal axis of each elongated elements is substantially parallel to one another, wherein, the size of described main body is substantially determined by the quantity of elongated elements in described array and layout；And
At least partly surround the prefabricated plastic skin members of multiple elongated elements in described array,
Wherein, described skin members includes the first epidermis element and the second epidermis element, described first epidermis element has recessed form, described second epidermis element is arranged to be assemblied in described first epidermis element so that described skin members can be configured to accommodate variable number and the layout of elongated elements in described array.
2. modular fibre reinforced plastics flange as claimed in claim 1, wherein, described skin members is entirely around the array of described elongated elements.
3. modular fibre reinforced plastics flange as claimed in claim 1 or 2, wherein, described second skin members includes socket to accommodate shear web in use.
4. modular fibre reinforced plastics flange as claimed in claim 1 or 2, wherein, at least two elongated elements in the plurality of elongated elements includes different materials.
5. modular fibre reinforced plastics flange as claimed in claim 1 or 2, also includes at least one enhancement layer being at least partially situated in the array of described elongated elements.
6. a structure composite beam, including:
Modular fibre reinforced plastics flange as described in any one in the claims；And
It is connected to the shear web on the skin members of described modular fibre reinforced plastics flange.
7. structure composite beam as claimed in claim 6, wherein, described shear web includes the structural core between two composite layers.
8. the method forming the modular fibre reinforced plastics flange for structure composite beam, including:
The main body formed with multiple prefabricated elongated elements, the plurality of elongated elements is arranged to array so that the longitudinal axis of each elongated elements is substantially parallel to one another, and wherein, the size of described main body is substantially determined by the quantity of elongated elements in described array and layout；And
Prefabricated skin members is connected in described main body so that described skin members at least partly surrounds the multiple elongated elements in described array；
Wherein, described skin members includes the first epidermis element and the second epidermis element, described first epidermis element has recessed form, described second epidermis element is arranged to be assemblied in described first epidermis element so that described skin members can be configured to accommodate variable number and the layout of elongated elements in described array.
9. the method forming modular fibre reinforced plastics flange as claimed in claim 8, also includes:
The quantity of selection elongated elements and layout are to limit the size of described main body；And
Selecting skin members, this skin members is sized so as to the size of substantially engage described main body.
10. the method forming modular fibre reinforced plastics flange as claimed in claim 9, described method also includes:
Described main body is located in described first epidermis element；And
To form the skin members entirely around described main body in described second epidermis element is located at described first epidermis element.
The method forming modular fibre reinforced plastics flange as described in any one in 11. such as claim 8 to 10, wherein, each ingredient of described modular fibre reinforced plastics flange is made with continuous working system.
The method forming modular fibre reinforced plastics flange as described in any one in 12. such as claim 8 to 10, wherein, before implementing described method, elongated elements and the skin members of described modular fibre reinforced plastics flange are in solid state or semi-cured state and present their final form.
13. 1 kinds of methods forming structure composite beam, including:
The method described in any one in claim 8 to 10 is utilized to form modular fibre reinforced plastics flange；And
At least one shear web is connected on the skin members of described modular fibre reinforced plastics flange.
14. methods forming structure composite beam as claimed in claim 13, wherein, each ingredient of described structure composite beam is made with continuous working system.
15. methods forming structure composite beams as described in claim 13 or 14, wherein, are implementing before described method, and at least one shear web described of described structure composite beam is all in solid state or semi-cured state the final form presenting them.
16. 1 kinds of kits being used for forming modular fibre reinforced plastics flange, including:
Suitably forming multiple elongated elements of main body, described main body includes the multiple elongated elements being arranged to array, and wherein, the longitudinal axis of each elongated elements is substantially parallel to one another；And
Multiple skin members, wherein, the plurality of skin members is sized so as to corresponding with the predetermined quantity of elongated elements；
Wherein, described skin members includes the first epidermis element and the second epidermis element, described first epidermis element has recessed form, described second epidermis element is arranged to be assemblied in described first epidermis element so that described skin members can be configured to accommodate variable number and the layout of elongated elements in described array.
17. kits as claimed in claim 16, wherein, described elongated elements and described skin members are in solid state or semi-cured state and present their final form.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GBGB1007336.9A GB201007336D0 (en) | 2010-04-30 | 2010-04-30 | A modular structural composite beam |
| GB1007336.9 | 2010-04-30 | ||
| PCT/GB2011/000661 WO2011135306A1 (en) | 2010-04-30 | 2011-04-28 | A modular structural composite beam |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103003060A CN103003060A (en) | 2013-03-27 |
| CN103003060B true CN103003060B (en) | 2016-12-07 |
Family
ID=42289971
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201180028703.XA Active CN103003060B (en) | 2010-04-30 | 2011-04-28 | Modular organization composite beam |
Country Status (10)
| Country | Link |
|---|---|
| US (3) | US8905718B2 (en) |
| EP (3) | EP2563573B1 (en) |
| JP (1) | JP5778758B2 (en) |
| CN (1) | CN103003060B (en) |
| BR (1) | BR112012027792A2 (en) |
| DK (2) | DK2617557T3 (en) |
| ES (2) | ES2668790T3 (en) |
| GB (1) | GB201007336D0 (en) |
| PL (1) | PL2617558T3 (en) |
| WO (1) | WO2011135306A1 (en) |
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Also Published As
| Publication number | Publication date |
|---|---|
| US9567749B2 (en) | 2017-02-14 |
| EP2563573A1 (en) | 2013-03-06 |
| EP2617557B1 (en) | 2019-12-11 |
| US9290941B2 (en) | 2016-03-22 |
| PL2617558T3 (en) | 2018-07-31 |
| CN103003060A (en) | 2013-03-27 |
| US20130340384A1 (en) | 2013-12-26 |
| JP2013529145A (en) | 2013-07-18 |
| EP2617557A1 (en) | 2013-07-24 |
| ES2668790T3 (en) | 2018-05-22 |
| EP2617558A1 (en) | 2013-07-24 |
| WO2011135306A1 (en) | 2011-11-03 |
| US20130055677A1 (en) | 2013-03-07 |
| US20130340385A1 (en) | 2013-12-26 |
| BR112012027792A2 (en) | 2016-08-02 |
| JP5778758B2 (en) | 2015-09-16 |
| GB201007336D0 (en) | 2010-06-16 |
| EP2617558B1 (en) | 2018-04-18 |
| DK2617557T3 (en) | 2020-03-16 |
| ES2766824T3 (en) | 2020-06-15 |
| US8905718B2 (en) | 2014-12-09 |
| DK2617558T3 (en) | 2018-05-28 |
| EP2563573B1 (en) | 2020-09-30 |
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